RU2016119155A - GAS-TURBINE INSTALLATION EQUIPPED WITH MEANS OF TRANSMISSION OF PERFORMANCE OF TRACTION OF ITS ENGINE - Google Patents

GAS-TURBINE INSTALLATION EQUIPPED WITH MEANS OF TRANSMISSION OF PERFORMANCE OF TRACTION OF ITS ENGINE Download PDF

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RU2016119155A
RU2016119155A RU2016119155A RU2016119155A RU2016119155A RU 2016119155 A RU2016119155 A RU 2016119155A RU 2016119155 A RU2016119155 A RU 2016119155A RU 2016119155 A RU2016119155 A RU 2016119155A RU 2016119155 A RU2016119155 A RU 2016119155A
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RU
Russia
Prior art keywords
gas turbine
turbine installation
crankcase
installation according
rods
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RU2016119155A
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Russian (ru)
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RU2677312C2 (en
RU2016119155A3 (en
Inventor
Жереми Эдмон ФЕР
Кармен АНКЮТА
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Снекма
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Publication of RU2016119155A3 publication Critical patent/RU2016119155A3/ru
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • B64D27/40—
    • B64D27/406—
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines

Claims (15)

1. Газотурбинная установка, содержащая два конструктивных кольцевых картера (16,22), соединенные между собой при помощи средств (40,54) передачи усилий тяги двигателя, которые включают в себя штанги (54), отличающаяся тем, что указанные средства передачи усилий тяги дополнительно включают в себя по меньшей мере одну коробку (40,140,240) приводов агрегатов, которая закреплена на первом из упомянутых картеров (16) и которая соединена упомянутыми штангами с другим из упомянутых картеров (22).1. A gas turbine installation containing two structural annular crankcase (16,22), interconnected by means (40,54) of transmitting engine thrust forces, which include rods (54), characterized in that said means of transmitting thrust forces additionally include at least one box (40,140,240) of unit drives, which is mounted on the first of the said crankcases (16) and which is connected by said rods to another of the said crankcases (22). . Газотурбинная установка по п. 1, отличающаяся тем, что упомянутая по меньшей мере одна коробка (40,140,240) приводов агрегатов закреплена на ступице (50) промежуточного картера (16).. A gas turbine installation according to claim 1, characterized in that the said at least one box (40,140,240) of the unit drives is mounted on the hub (50) of the intermediate housing (16). 3. Газотурбинная установка по п. 1 или 2, отличающаяся тем, что штанги (54) имеют первый конец, шарнирно соединенный с упомянутой по меньшей мере одной коробкой (40,140,240) приводов агрегатов, и второй конец, соединенный напрямую или опосредованно с межтурбинным картером (22) или с выпускным картером.3. A gas turbine installation according to claim 1 or 2, characterized in that the rods (54) have a first end pivotally connected to said at least one gearbox unit (40,140,240) and a second end connected directly or indirectly to the inter-turbine crankcase ( 22) or with an exhaust case. 4. Газотурбинная установка по п. 3, отличающаяся тем, что штанги (54) имеют второй конец, шарнирно соединенный с межтурбинным картером (22) или с выпускным картером.4. Gas turbine installation according to claim 3, characterized in that the rods (54) have a second end pivotally connected to the inter-turbine crankcase (22) or to the exhaust crankcase. 5. Газотурбинная установка по п. 3, отличающаяся тем, что штанги (54) имеют второй конец, соединенный с межтурбинным картером (22) или с выпускным картером при помощи средств (30) задней подвески газотурбинной установки.5. Gas turbine installation according to claim 3, characterized in that the rods (54) have a second end connected to the inter-turbine crankcase (22) or to the exhaust crankcase using means (30) of the rear suspension of the gas turbine installation. 6. Газотурбинная установка по п. 5, отличающаяся тем, что штанги (54) имеют второй конец, шарнирно соединенный со средствами (30) подвески, которые установлены на упомянутом межтурбинном или выпускном картере.6. Gas turbine installation according to claim 5, characterized in that the rods (54) have a second end pivotally connected to the suspension means (30) that are mounted on said inter-turbine or exhaust crankcase. 7. Газотурбинная установка по п. 5 или 6, отличающаяся тем, что средства (30) подвески содержат кронштейн (31), выполненный с возможностью крепления на пилоне летательного аппарата.7. Gas turbine installation according to claim 5 or 6, characterized in that the suspension means (30) comprise a bracket (31) made with the possibility of mounting on an aircraft pylon. 8. Газотурбинная установка по одному из пп. 1-6, отличающаяся тем, что средства передачи усилий штанги содержат только одну коробку (40) приводов агрегатов, которая имеет общую форму в виде V или U и которая содержит две боковые стойки (46), соединенные между собой срединной частью (48), причем эта срединная часть закреплена на упомянутом первом картере (16), и каждая из стоек соединена штангой (54) с другим картером (22).8. Gas turbine installation according to one of paragraphs. 1-6, characterized in that the means of transmission of the force of the rod contain only one box (40) of drive units, which has a common shape in the form of V or U and which contains two side racks (46), interconnected by the middle part (48), moreover, this middle part is fixed on the aforementioned first crankcase (16), and each of the racks is connected by a rod (54) with another crankcase (22). 9. Газотурбинная установка по одному из пп. 1-7, отличающаяся тем, что средства передачи усилий тяги содержат две независимые коробки (140, 240) приводов агрегатов, имеющие удлиненную форму, при этом каждая коробка приводов агрегатов содержит продольный конец, закрепленный на первом картере (16), и противоположный продольный конец, соединенный штангой (54) с другим картером (22).9. Gas turbine installation according to one of paragraphs. 1-7, characterized in that the means of transmitting thrust forces contain two independent boxes (140, 240) of drive units, having an elongated shape, with each box drive units contains a longitudinal end mounted on the first crankcase (16), and the opposite longitudinal end connected by a rod (54) to another crankcase (22). 10. Газотурбинная установка по одному из пп. 1-9, отличающаяся тем, что штанги (54) являются по существу параллельными между собой и относительно продольной оси газотурбинной установки.10. Gas turbine installation according to one of paragraphs. 1-9, characterized in that the rods (54) are essentially parallel to each other and relative to the longitudinal axis of the gas turbine installation. 11. Газотурбинная установка по одному из пп. 1-10, отличающаяся тем, что каждая штанга (54) содержит первый конец, шарнирно соединенный с проушиной (58), неподвижно соединенной с картером (44) упомянутой по меньшей мере одной коробки (40) приводов агрегатов, и второй конец, шарнирно соединенный с проушиной (60), неподвижно соединенной с органом (31,56), установленным на упомянутом другом картере (22).11. Gas turbine installation according to one of paragraphs. 1-10, characterized in that each rod (54) comprises a first end pivotally connected to an eye (58) fixedly connected to the crankcase (44) of the at least one gearbox drive unit (40), and a second end pivotally connected with an eye (60) fixedly connected to an organ (31.56) mounted on said other crankcase (22). 12. Газотурбинная установка по п. 11, отличающаяся тем, что орган представляет собой кольцо (56), которое установлено вокруг упомянутого другого картера и на котором установлены средства (30) подвески газотурбинной установки на пилоне летательного аппарата.12. A gas turbine installation according to claim 11, characterized in that the organ is a ring (56), which is installed around said other crankcase and on which means (30) are mounted for suspending the gas turbine installation on an aircraft pylon. 13. Газотурбинная установка по п. 11, отличающаяся тем, что орган представляет собой кронштейн (31) для крепления средств подвески газотурбинной установки на пилоне летательного аппарата.13. A gas turbine installation according to claim 11, characterized in that the organ is a bracket (31) for fastening the suspension means of the gas turbine installation to the pylon of the aircraft. 14. Использование по меньшей мере одной коробки (40,140,240) приводов агрегатов газотурбинной установки для передачи усилий тяги двигателя этой газотурбинной установки.14. The use of at least one box (40,140,240) of the drive units of the gas turbine installation to transmit the thrust of the engine of this gas turbine installation. 15. Коробка (40,140,240) приводов агрегатов газотурбинной установки, содержащая картер (44), на котором выполнены средства (52) крепления на газотурбинной установке и средства соединения с штангами (54), отличающаяся тем, что картер является конструктивным для обеспечения передачи усилия между средствами крепления и средствами соединения. 15. A box (40,140,240) of drive units of a gas turbine installation, comprising a crankcase (44), on which there are made means (52) of fastening on a gas turbine installation and means of connecting with rods (54), characterized in that the crankcase is structural for ensuring the transfer of force between the means fastenings and means of connection.
RU2016119155A 2013-11-07 2014-11-06 Turbine engine provided with means of absorbing stresses from thrust of engine thereof RU2677312C2 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1360904 2013-11-07
FR1360904A FR3012845B1 (en) 2013-11-07 2013-11-07 TURBOMACHINE EQUIPPED WITH MEANS FOR RECOVERING THE THROTTLE EFFORTS OF ITS ENGINE
PCT/FR2014/052847 WO2015067906A1 (en) 2013-11-07 2014-11-06 Turbine engine provided with means for absorbing stresses from the thrust of the engine thereof

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Publication Number Publication Date
RU2016119155A true RU2016119155A (en) 2017-12-08
RU2016119155A3 RU2016119155A3 (en) 2018-07-13
RU2677312C2 RU2677312C2 (en) 2019-01-16

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RU2016119155A RU2677312C2 (en) 2013-11-07 2014-11-06 Turbine engine provided with means of absorbing stresses from thrust of engine thereof

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US (1) US10287984B2 (en)
EP (1) EP3066320B1 (en)
CN (1) CN105793543B (en)
BR (1) BR112016010063B1 (en)
CA (1) CA2928696C (en)
FR (1) FR3012845B1 (en)
RU (1) RU2677312C2 (en)
WO (1) WO2015067906A1 (en)

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WO2015067906A1 (en) 2015-05-14
EP3066320A1 (en) 2016-09-14
FR3012845B1 (en) 2015-10-23
RU2677312C2 (en) 2019-01-16
RU2016119155A3 (en) 2018-07-13
US20160281605A1 (en) 2016-09-29
US10287984B2 (en) 2019-05-14
CA2928696A1 (en) 2015-05-14
BR112016010063A2 (en) 2017-08-01
CN105793543B (en) 2019-03-05
EP3066320B1 (en) 2021-12-29
FR3012845A1 (en) 2015-05-08
CN105793543A (en) 2016-07-20
CA2928696C (en) 2022-07-19
BR112016010063B1 (en) 2022-02-01

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